(Solution Download) A supersonic aircraft flies at M{ = 2.7 at 20 km altitude on a standard day. Air enters the engine..


A supersonic aircraft flies at M{ = 2.7 at 20 km altitude on a standard day. Air enters
the engine inlet system where it is slowed isentropically to M2 = 1.3. A normal shock
occurs at that location. The resulting subsonic flow is decelerated further to M4 = 0.40.
The subsonic diffusion is adiabatic but not isentropic; the final pressure is 104 kPa
(abs). Evaluate (a) the stagnation temperature for the flow, (b) the pressure change
across the shock, (c) the entropy change, ^4 ? 5-,, and (d) the final stagnation pressure.
Sketch the process path on a Ts diagram, indicating all static and stagnation states,

 







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